DE639867C - Multi-stage internal combustion turbine in two-flow design for operation with atomized or gaseous fuels - Google Patents

Description

Multi-stage internal combustion turbine in two-flow design for operation with atomized or gaseous fuels The present invention aims to use cheaper, high-quality fuels, with high thermal efficiency, for economic Kiafterzeugung in internal combustion turbines, the simple design, low weight and quiet gait, with high operational reliability surpassing the piston engines and are particularly suitable for direct drive due to their high speed.

In the known piston engines occur in the compression and Work cycle to strong impacts, the high mechanical stress, especially the Housing, bearings and foundations. With the continuously acted Two-flow internal combustion turbines avoid these disadvantages.

The suction, compression and extension cycles of the piston engines consume power; they worsen the mechanical efficiency and result in uneven running. These losses , which are converted into heat, therefore reduce the performance. In the case of internal combustion turbines of the two-flow design, as with other turbines, as a result of uninterrupted loading, a smooth, even run with good mechanical efficiency and therefore low fuel consumption occurs.

The unbalanced gear of the piston engine results in large centrifugal masses to achieve a useful degree of uniformity; due to the even run the internal combustion turbines do not require special flywheels.

In order to simplify the design, the invention consists in that in one is provided between the two turbine nozzles acted upon in the two-flow fixed annular body combustion chambers are arranged, whose to the outlet of the propellant gases serving openings in the axial direction on both sides of the ring body and their radially inwardly directed, the air supply opening through with 'the Runner rotating turbine parts, e.g. B. WeUenausnehmungen or cover plates of the Combustion chambers, while being controlled radially from the outside into those with inlet nozzles provided ignition pre-chambers in which the combustion is initiated, fuel valve-e open with atomizing nozzle.

The dimensions and weights of the internal combustion turbine are small. - The internal combustion turbine described below with compressed air supply for charging and purging and automatic heating of the combustion air with the controlled combustion chamber charge and gas expansion ensured, with the gas engines such. B. Diesel engines, proven - known auxiliary devices, such as fuel pumps, gas mixing valves, air compressors, power regulators and electrical starter and ignition devices, equipped, full operational safety with a simple and lightweight design.

Description of the internal combustion turbine in two-flow design The drawing illustrates one embodiment.

In Fig. I the turbine is shown in the longitudinal direction, the upper one Part in section with open firing canine, lower half partly in section, partly in Opinion.

Fig. 2 shows in the upper part a cross section of the turbine, to the left through the turbine chamber according SchnittA-B, right through the closed 'combustor according SchnittC-D, irn lower part is a view of the turbine.

Fig. 3 to 5 show turbine parts on a large scale, namely Fig. 3 turbine center (longitudinal section) with pulled out impeller, above with open, below with closed combustion chamber. Fig. 4 illustrates, shown rolled up, the combustion chamber cross section with subsequent first impeller stage according to section E-F. Fig. 5 shows in the left half above a view of the impeller, below the combustion chamber ring, in the right half above a cross section through the blades according to section 1-1 (, below a cross section through the blades according to Section O-H.

The internal combustion turbine in Zweiflußbauart consists essentially of the following parts: Wassergekühltein Gehäusea with bearings hollow Welleb with compressed air channels bl, b, two #ymnietrischen Läufernd with Brennkarnmerabschluß 1 and i, with water-cooled Läufermantelk Brennkammerringm and waste gas chambers s..

The two-part water-cooled housing a has operating openings for fuel valves and spark or glow plugs.

The shaft b is bored hollow up to the end of the jacket and has cold compressed air outflow openings b for combustion air, which open into both cavities e of the rotor body d , and b. for cooling and purging air that end in the exhaust gas cells via a cooling line and for cooling. the shaft - b and exhaust chambers s and serve to flush the latter. In addition, the hollow shaft b has recesses in the center of the turbine for the combustion air supply line to the combustion chambers.

The individual rotor bodies d, arranged in a two-flow design, are fastened on the shaft b and contain cavities in the interior which are connected to the shaft recesses c in the center of the turbine by hot air ducts f . The combustion air is passed through this to the combustion chimneysxn; i through radial, conical ducts.

Furthermore, the cavities in the runner -: # are physically connected to the propellant gasesäl # -n in the #, "e." Scooping through small, the scavenging air the - .., P ## de channels g .

- The heat in the cavities by the internal turbine heat Compressed air flows into the combustion chambers it via shaft recess c and air duct o from both halves of the turbine, the air supply through the circumferential shaft recess c and fixed opening of the combustion chamber ring m is controlled, the bearing-like the wave closes tightly.

This Drennkammerluftzuführungskanäle o are closed by FFIE position of the shaft to Brennkammeriing during combustion, on the other hand open to the new charge of hot-Prennungsluft Ver.

To transfer the propellant gases from one to the other impeller stage, spiral cutouts 1 in the jacket k and slot opening h in the rotor body d can be used, while the outer cells of the rotor open out into exhaust gas rings.

The blading of the first pressure stage in the middle of the turbine the two-flow combustion chamber controls the propellant gas outlet from the combustion chamber ii either by centrically engaging end disks with passage slots in the combustion chamber ring j (Fig. 3 below) or, as shown in Fig. 4, directly through the corresponding shape of the turbine blades i. Both close the combustion chambers like a rotary valve when charged with hot air and open them after ignition to force-generating relaxation of the propellant gases.

The rotor bodies of the internal combustion turbine are on the housing a fastened two-part, with cooling channels given away Mantelk surrounded by means Stuffing box is sealed against the shaft. The jacket is used for further cooling of water around # flowed.

The mantlek has in its center a shear, yam-shaped fuel ring attached to the mantle with ignition pre-chambers p. Radially from the outside in this lead the Brennstoffveiitileq provided with fuel injectors and, for electrical ignition, spark or glow plugs, currencies, 'end Düsenp the atria, in which the -Cremation is initiated connect with the radially Brennkammernn.

The radial, inwardly leading hot-pressure air supply openings o open onto the shaft and are controlled by the recesses c of the shaft, d. H. connected to the hot air cavities via outlet ducts or separated from them - depending on the position, the recess for the combustion chamber inlet opening.

The combustion chambers t # have gas outlet openings til on b. # Iden with a slot in the axial direction. Sides --- of the ring body (Fig. 4) Z ' transferring the propellant gases into the impeller blading, in the combustion chamber ring m are, -as said above., Connect the slide-like end surfaces of the first pressure stage i and i centrally.d and sealingly guided. Synimetrically arranged spiral-shaped recesses 1 in the casing serve when the gases are relaxed to transfer them from the tiner to the other pressure stage of the impellers.

At the ends of each Mantelk carries an annular exhaust Kammer which the waste gases in that conduct collecting spaces a. At. this Sigd the outlet connection v and - connected exhaust tube.

The outer rotor bodies d contain open slots, -which conduct the exhaust gases into the chambers s : . - by means of cold air smoothly D b of the shaft bore, as shown, above - said continuously purged exhaust chambers and cooled, wherein the built-Kühlkammernt of preventing the excessive heating of the bearings proximal shaft piece.

Through free space wipe housing and a z-k sheath -can order energetic - cooling of the turbine and the Lagger Kühlwass # he be passed; in this case, the intended cooling of the housing a through channels can be omitted; however, the cooling of the jacket remains through the channels. Working process of the internal combustion turbine In addition to the parts of the turbine contained in the drawings (injection valves and glow or spark plugs), the following known accessories belong to the turbine - a small compressor coupled to the shaft to generate the necessary. Compressed air, a centrifugal governor for regulating the speed, a fuel pump for liquid fuels or a gas-mixing valve for gaseous fuels.

The controller regulates the amount of fuel or the gas mixture accordingly the burden.

In addition, the turbine requires the well-known electrical starter device (e.g. starter).

All devices are driven by the shaft in a known manner and controlled.

Eat-deviates from the quantities of compressed air constantly pressed into the hollow shaft. a small part through bores, # 2 in the cooling cells t of the waste gas ... and cools -here the storage and waste gas cells and flushes the latter. Most of the compressed air flows - through the openings, b, into the two hollow spaces, the impeller hub and. is heated up by the internal waste heat - the rotor, but at the same time cools the shaft - and prevents impermissible increases in temperature - the same. A small part of this hot compressed air escapes through the bores into the blades and flushes them of exhaust gases, while the rest as combustion air on each side via the shaft recess c through the radial channels o controlled by the shaft b into the combustion chamber occurs.

The combustion combs are closed by the tightly connected, sealed rotary valve-like end disks or surfaces! the inner impeller stage is completely closed or open on both sides, depending on the position of the non-running turbine parts. So they are automatically controlled in such a way that with -geöffhe th Heißdrucl -luftkanäleo -during the fuel injection and ignition the outlet slots, ii, the 'combustion chambers are akial closed, but are opened after ignition to force-generating relaxation of the gases, with the hot air channels o, controlled - by the rotating shaft b, are closed.

While the combustion chamber outlet slots ii are closed by the rotary valves j and i, shortly after they have been charged with hot compressed air, finely atomized fuel is injected under pressure from the valve nozzle q into the ignition pre-chambers p and at the same time through the hot compressed air or with the help of the glow or spark plugs to ignite brought.

When the turbine is operated with gaseous fuels, the Place of the fuel atomizer valve q a gas valve that releases the pressurized, Gas from the gas generator mixed with combustion air in the mixing valve into the ignition chamber presses where it ignites by means of spark plugs or appropriate glow plugs will. The mixing valve is controlled in a known manner by the centrifugal governor.

The fuel ignited in the antechambers p enters the combustion chambers n under a considerable increase in pressure through nozzles and, after opening the same, acts on both sides through the controlled rotary valve-like closures t and i on the blades of the impellers by releasing the gases, performing work with a drop in pressure, whereupon the partially relaxed gases are passed through the recess 1 of the jacket k into the second pressure stages for work performance, whereby the gases act on the blading and pass through slit openings k to the third chamber.

The same process, always associated with further relaxation of the gases, repeats itself in the third and fourth pressure stage, whereupon the gases with low overpressure in the exhaust gas # lower s and collecting chamber u and this -through the Leave the outlet pipe socket il.

The cold turbine is started by means of a starter motor, with the first ignitions being initiated by known ignition devices. The turbine output can also be controlled by switching injection nozzles on and off.

Claims (2)

PATENT CLAIMS: i. Multi-stage internal combustion turbine in two-flow design for operation with atomized or gaseous fuels with hot-pressure air ignition or electrical ignition together with a water-cooled housing and hollow shaft, which is used to supply the combustion air and the cooling air for the rotor, characterized in that in one provided between the two two-flow acted upon turbine parts fixed ring body (s) combustion chambers (n) are arranged, whose openings (n,) serving for the outlet of the propellant gases in the axial direction on both sides of the ring body and whose radially inwardly directed, air supply opening (o) through with the 'fer rotating turbine parts, z. B. shaft recesses (c) or end plates of the combustion chambers, controlled we j rden, while radially from the outside in the ignition pre-chambers (p) 2 in which the combustion is initiated with inlet nozzles, fuel valves with atomizing nozzle (q) open. 2. Internal combustion turbine according to claim. i, characterized in that the radially inwardly directed opening (o) serving for the air supply is controlled by the shaft (b) serving for the compressed air supply, in which there are recesses (c) which are filled with highly heated compressed air from the cavities ( e) the rotor body flowing, are fed. 3. internal combustion turbine according to claim 2, characterized in that the cavities (s) of the rotor body are connected to the fuel gas channels in the blading .by small channels (g), which lead to the scavenging air blowing gas channels. 4. Internal combustion turbine according to claim i and 3, characterized in that by. the hollow shaft (b) cold compressed air is passed via cooling chambers (1) also to the exhaust gas chambers (s), which are thereby cleaned and flushed, the cooling chambers serving to cool the annular exhaust gas chambers - and shaft.